GOE 679 AIRFOIL (goe679-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 679 AIRFOIL (goe679-il) Reynolds number: 500,000 Max Cl/Cd: 76.26 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe679-il-500000.txt Download as CSV file: xf-goe679-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 679 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.7354 0.09341 0.08992 -0.0723 1.0000 0.0387
-16.500 -0.7937 0.08122 0.07747 -0.0799 1.0000 0.0385
-16.250 -0.8305 0.07320 0.06927 -0.0845 1.0000 0.0385
-16.000 -0.8572 0.06698 0.06290 -0.0877 1.0000 0.0384
-15.750 -0.8822 0.06116 0.05692 -0.0908 1.0000 0.0385
-15.500 -0.9021 0.05630 0.05193 -0.0930 1.0000 0.0385
-15.250 -0.9190 0.05210 0.04760 -0.0945 1.0000 0.0385
-15.000 -0.9359 0.04826 0.04364 -0.0957 1.0000 0.0387
-14.750 -0.9534 0.04487 0.04011 -0.0961 1.0000 0.0388
-14.500 -0.9678 0.04226 0.03740 -0.0954 1.0000 0.0389
-14.250 -0.9644 0.03959 0.03458 -0.0976 0.9979 0.0390
-14.000 -0.9531 0.03737 0.03218 -0.1004 0.9945 0.0392
-13.750 -0.9395 0.03566 0.03032 -0.1021 0.9913 0.0393
-13.500 -0.9266 0.03364 0.02824 -0.1025 0.9871 0.0397
-13.250 -0.9069 0.03214 0.02671 -0.1036 0.9839 0.0400
-13.000 -0.8834 0.03095 0.02548 -0.1050 0.9817 0.0403
-12.750 -0.8714 0.02985 0.02434 -0.1038 0.9760 0.0406
-12.500 -0.8522 0.02888 0.02332 -0.1037 0.9718 0.0409
-12.250 -0.8272 0.02789 0.02228 -0.1045 0.9694 0.0413
-12.000 -0.8092 0.02698 0.02132 -0.1037 0.9641 0.0416
-11.750 -0.7870 0.02602 0.02029 -0.1036 0.9593 0.0421
-11.500 -0.7579 0.02506 0.01926 -0.1047 0.9569 0.0425
-11.250 -0.7269 0.02417 0.01830 -0.1060 0.9552 0.0430
-11.000 -0.7126 0.02341 0.01747 -0.1039 0.9475 0.0434
-10.750 -0.6837 0.02264 0.01662 -0.1045 0.9442 0.0438
-10.500 -0.6553 0.02144 0.01543 -0.1054 0.9420 0.0447
-10.250 -0.6231 0.02054 0.01453 -0.1068 0.9405 0.0454
-10.000 -0.6113 0.01989 0.01386 -0.1039 0.9309 0.0458
-9.750 -0.5801 0.01913 0.01307 -0.1048 0.9284 0.0466
-9.500 -0.5450 0.01832 0.01222 -0.1063 0.9265 0.0475
-9.250 -0.5263 0.01768 0.01152 -0.1044 0.9173 0.0482
-9.000 -0.4957 0.01692 0.01071 -0.1049 0.9129 0.0490
-8.750 -0.4639 0.01600 0.00980 -0.1059 0.9101 0.0503
-8.500 -0.4479 0.01550 0.00928 -0.1034 0.8993 0.0512
-8.250 -0.4133 0.01490 0.00864 -0.1047 0.8952 0.0529
-8.000 -0.3857 0.01441 0.00810 -0.1046 0.8868 0.0544
-7.750 -0.3513 0.01375 0.00745 -0.1060 0.8802 0.0570
-7.500 -0.3114 0.01321 0.00687 -0.1085 0.8739 0.0607
-7.250 -0.2781 0.01272 0.00637 -0.1096 0.8643 0.0661
-7.000 -0.2348 0.01212 0.00583 -0.1130 0.8571 0.0784
-6.750 -0.2009 0.01170 0.00548 -0.1143 0.8459 0.0981
-6.500 -0.1645 0.01148 0.00527 -0.1160 0.8358 0.1135
-6.250 -0.1311 0.01135 0.00511 -0.1170 0.8253 0.1233
-6.000 -0.1025 0.01125 0.00498 -0.1170 0.8151 0.1306
-5.750 -0.0714 0.01123 0.00486 -0.1174 0.8049 0.1374
-5.500 -0.0480 0.01112 0.00475 -0.1163 0.7949 0.1433
-5.250 -0.0199 0.01110 0.00466 -0.1162 0.7851 0.1491
-5.000 0.0025 0.01101 0.00454 -0.1148 0.7760 0.1539
-4.750 0.0271 0.01094 0.00445 -0.1140 0.7666 0.1591
-4.500 0.0507 0.01092 0.00437 -0.1128 0.7575 0.1637
-4.250 0.0729 0.01082 0.00424 -0.1115 0.7476 0.1685
-4.000 0.0955 0.01075 0.00416 -0.1102 0.7384 0.1737
-3.750 0.1177 0.01073 0.00409 -0.1087 0.7286 0.1789
-3.500 0.1398 0.01064 0.00399 -0.1073 0.7193 0.1858
-3.250 0.1602 0.01060 0.00394 -0.1055 0.7085 0.1924
-3.000 0.1816 0.01058 0.00386 -0.1039 0.6980 0.1984
-2.750 0.2004 0.01048 0.00377 -0.1019 0.6863 0.2053
-2.500 0.2203 0.01046 0.00371 -0.0999 0.6748 0.2118
-2.250 0.2386 0.01041 0.00361 -0.0977 0.6620 0.2185
-2.000 0.2535 0.01033 0.00353 -0.0948 0.6479 0.2250
-1.750 0.2699 0.01032 0.00346 -0.0921 0.6332 0.2313
-1.500 0.2851 0.01026 0.00339 -0.0892 0.6176 0.2395
-1.250 0.3007 0.01028 0.00334 -0.0865 0.6006 0.2481
-1.000 0.3161 0.01031 0.00331 -0.0837 0.5832 0.2569
-0.750 0.3320 0.01036 0.00331 -0.0810 0.5659 0.2671
-0.500 0.3493 0.01041 0.00332 -0.0787 0.5503 0.2777
-0.250 0.3671 0.01049 0.00336 -0.0765 0.5354 0.2898
0.000 0.3846 0.01057 0.00341 -0.0742 0.5220 0.3028
0.250 0.4033 0.01065 0.00346 -0.0722 0.5094 0.3168
0.500 0.4227 0.01071 0.00352 -0.0704 0.4984 0.3327
0.750 0.4408 0.01078 0.00359 -0.0683 0.4882 0.3521
1.000 0.4607 0.01080 0.00366 -0.0666 0.4798 0.3754
1.250 0.4794 0.01081 0.00374 -0.0646 0.4716 0.4054
1.500 0.4970 0.01079 0.00384 -0.0625 0.4639 0.4515
1.750 0.5134 0.01065 0.00395 -0.0601 0.4569 0.5266
2.000 0.5242 0.01044 0.00408 -0.0566 0.4505 0.6408
2.250 0.5329 0.01012 0.00426 -0.0523 0.4448 0.7890
2.500 0.6927 0.01059 0.00496 -0.0802 0.4301 0.9575
2.750 0.7335 0.01087 0.00519 -0.0828 0.4234 0.9775
3.000 0.7794 0.01115 0.00540 -0.0866 0.4158 0.9891
3.250 0.8244 0.01151 0.00565 -0.0903 0.4081 0.9975
3.500 0.8617 0.01165 0.00577 -0.0923 0.4024 1.0000
3.750 0.8740 0.01175 0.00584 -0.0893 0.3970 1.0000
4.000 0.8859 0.01192 0.00594 -0.0861 0.3916 1.0000
4.250 0.9008 0.01205 0.00605 -0.0835 0.3864 1.0000
4.500 0.9169 0.01217 0.00615 -0.0812 0.3810 1.0000
4.750 0.9319 0.01234 0.00628 -0.0787 0.3757 1.0000
5.000 0.9461 0.01258 0.00645 -0.0761 0.3703 1.0000
5.250 0.9645 0.01269 0.00659 -0.0742 0.3655 1.0000
5.500 0.9815 0.01287 0.00675 -0.0721 0.3599 1.0000
5.750 0.9966 0.01313 0.00694 -0.0698 0.3542 1.0000
6.000 1.0144 0.01333 0.00714 -0.0679 0.3488 1.0000
6.250 1.0323 0.01354 0.00734 -0.0661 0.3429 1.0000
6.500 1.0479 0.01383 0.00757 -0.0639 0.3365 1.0000
6.750 1.0657 0.01408 0.00782 -0.0621 0.3308 1.0000
7.000 1.0835 0.01434 0.00807 -0.0604 0.3247 1.0000
7.250 1.0991 0.01469 0.00837 -0.0584 0.3185 1.0000
7.500 1.1171 0.01499 0.00867 -0.0568 0.3126 1.0000
7.750 1.1343 0.01531 0.00898 -0.0551 0.3064 1.0000
8.000 1.1484 0.01577 0.00937 -0.0529 0.2999 1.0000
8.250 1.1671 0.01608 0.00971 -0.0515 0.2940 1.0000
8.500 1.1825 0.01652 0.01011 -0.0497 0.2872 1.0000
8.750 1.1971 0.01702 0.01057 -0.0478 0.2809 1.0000
9.000 1.2145 0.01742 0.01099 -0.0464 0.2752 1.0000
9.250 1.2286 0.01797 0.01150 -0.0445 0.2694 1.0000
9.500 1.2434 0.01852 0.01204 -0.0428 0.2639 1.0000
9.750 1.2598 0.01901 0.01254 -0.0414 0.2587 1.0000
10.000 1.2736 0.01964 0.01315 -0.0397 0.2536 1.0000
10.250 1.2859 0.02037 0.01385 -0.0379 0.2490 1.0000
10.500 1.3031 0.02088 0.01440 -0.0367 0.2454 1.0000
10.750 1.3180 0.02151 0.01505 -0.0353 0.2414 1.0000
11.000 1.3306 0.02229 0.01582 -0.0338 0.2377 1.0000
11.250 1.3414 0.02320 0.01670 -0.0320 0.2337 1.0000
11.500 1.3579 0.02381 0.01737 -0.0310 0.2309 1.0000
11.750 1.3725 0.02453 0.01813 -0.0298 0.2275 1.0000
12.000 1.3850 0.02540 0.01901 -0.0285 0.2241 1.0000
12.250 1.3953 0.02644 0.02002 -0.0270 0.2207 1.0000
12.500 1.4068 0.02741 0.02101 -0.0257 0.2177 1.0000
12.750 1.4214 0.02823 0.02189 -0.0248 0.2155 1.0000
13.000 1.4347 0.02913 0.02285 -0.0238 0.2128 1.0000
13.250 1.4462 0.03017 0.02391 -0.0227 0.2100 1.0000
13.500 1.4558 0.03136 0.02510 -0.0215 0.2072 1.0000
13.750 1.4635 0.03269 0.02641 -0.0202 0.2039 1.0000
14.000 1.4761 0.03374 0.02754 -0.0194 0.2020 1.0000
14.250 1.4881 0.03483 0.02871 -0.0186 0.1999 1.0000
14.500 1.4989 0.03603 0.02996 -0.0178 0.1978 1.0000
14.750 1.5086 0.03732 0.03130 -0.0170 0.1954 1.0000
15.000 1.5162 0.03882 0.03281 -0.0161 0.1931 1.0000
15.250 1.5234 0.04032 0.03431 -0.0152 0.1907 1.0000
15.500 1.5316 0.04178 0.03581 -0.0144 0.1886 1.0000
15.750 1.5412 0.04321 0.03734 -0.0138 0.1867 1.0000
16.000 1.5491 0.04480 0.03901 -0.0133 0.1847 1.0000
16.250 1.5568 0.04642 0.04069 -0.0127 0.1825 1.0000
16.500 1.5624 0.04826 0.04257 -0.0122 0.1803 1.0000
16.750 1.5668 0.05020 0.04453 -0.0117 0.1779 1.0000
17.000 1.5714 0.05207 0.04640 -0.0111 0.1753 1.0000
17.250 1.5761 0.05418 0.04864 -0.0109 0.1732 1.0000
17.500 1.5804 0.05632 0.05087 -0.0108 0.1707 1.0000
17.750 1.5832 0.05864 0.05325 -0.0107 0.1683 1.0000
18.000 1.5831 0.06127 0.05590 -0.0106 0.1653 1.0000
18.250 1.5825 0.06388 0.05852 -0.0104 0.1621 1.0000
18.500 1.5833 0.06660 0.06137 -0.0107 0.1597 1.0000
18.750 1.5829 0.06943 0.06429 -0.0109 0.1566 1.0000
19.000 1.5802 0.07252 0.06742 -0.0112 0.1535 1.0000
19.250 1.5751 0.07584 0.07074 -0.0115 0.1505 1.0000
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